JAXA/NASA Products GuideBook · 2020. 9. 14. · ＊ This product was developed in the support of JAXA. ＊ Note that, with due to the rights of other relevant parties and/or depending

Products GuideBook

2020

Great selection

2020

ⓒJAXA/NASA

ⓒJAXA/NASA

MEISEI ELECTRIC CO., LTD.

Starting with the development of "Telemeter transmitting device" - Japan's first

electronic equipment installed in a rocket launched in 1955.

Meisei Electric has developed and manufactured more than 3,000 space-related

instruments since 1950’s.

Meisei Electric can provide all kinds of satellite components,

such as “Mission Equipment” and “Bus Components”.

We are developing CubeSat, Nano Satellites, and Micro

Satellites as well.

Outline

Capital Paid 3.0 billion Yen

Established in YR1938 (80-year history)

Listed in Tokyo Stock Exchange

Location

HQ & Factory: 2223 Naganuma-machi, Isesaki City, GUNMA 372-8585

Sales Office1-1, Toyosu 3-chome, Koto-ku, Tokyo 135-8115, Japan

Number of Employees

351 employees

(as at March 2020)

Sales

8.10 billion Yen

(consolidated for the year at March 2019)

ISO

9001

ISO

14001

HQ and Factory at Isesaki City Tokyo Branch


MEISEI’s Standard Nano &

Micro Satellite Bus Systems

• Meet the requirement for earth

observation missions

• Wide lineup ( 1U ~ 150kg class)

• COTS based engineering

< Micro Satellite Bus Components >

OBC Board for CubeSat

Magnetic

Torque

OBC

(Out of production)

GPS

Receiver 3 axis

Magnetometer

S band

Transceiver

Earth Sensor

Star Tracker

XTX

Space Particle Monitor Contamination Monitor

< Micro Satellite Mission Components>

3U Nano satellite

< Nano Satellite Components>

AIS Receiver

50kg piggy back structure


Meisei Electric Corp provides a new MEISEI Micro Satellite Bus System (M-SAT)

for Nano Satellite / Micro Satellite. M-ICU is the Compact-PCI based OBC and S-

band transceiver unit.

M-ICU (Prototype)

・ CompactPCI(cPCI) based Integrated Central Unit

・ High general versatility & scalability using

various card module

・Various card module available

(M-OBC, TC/TM, Power Control,

RF(S-band) module, I/F module etc.)

・Various I/F available

(Digital I/F: MIL-STD-1553B, CAN, RS422, LVDS, SpW

Analog I/F: AA，PA，AB，Current Out put)

・ Compact size

(WDH：222×205.6×145mm)

M-ICU

M-OBC Board

OBC Board

(Prototype) OBC Board Specifications

Dimension & weight 160 ×130 ×1.6 mm ,<170g

Power 3.3V, < 3W

Interface Compact PCI (32bit)

RS232C, SD card (for debug)

Option Board(cPCI) I/F Board (UART:12ch,GPIO:In 8ch Out 8ch)

STRX Board (S band wireless communication)

・ General purpose OBC board for Nano and Micro Satellite.

・3U CompactPCI(cPCI) Single Board Computer

・High Performance SH2A Processor

・2GB RAM ECC check on Data

・ 2.5MB ROM

・1GB User Flash Memory

・Dual-Redundant Boot

・Real Time Operating System available


• Own facilities for the Nano & micro satellite systems test

• Total support for the environmental tests for Nano & micro satellite

10tons Vibration

testing equipment

shock testing equipment

EMC shield room 3-Dimensional

X-ray inspection equipment

Diameter: 1.2m

Temp. control range: -180 to 200℃

*Temp. control accuracy(≦-100℃):N/A

Thermal vacuum chamber

Contracted Test Service


Features

Outline

64APSK: the highest frequency efficiency for earth observation downlink High-speed 522 Mbps downlink in less than 150 MHz frequency bandwidth Adaptive coding and modulation (69 Mbps to 522 Mbps) Low power consumption (22 watts) & Low mass (about 1.3 kg) Compatible with generic ground receiver (Zodiac Cortex HDR 4G) ITAR free Made in JAPAN

MTX-540X is a high-speed X band transmitter for the micro satellites. 64APSK technology achieves the world’s highest class frequency efficiency for the earth observation downlink. MTX-540X enables your satellites to maximum 522 Mbps downlink.

MEISEI ELECTRIC is provider of components and small satellite systems. Since 1955, MEISEI developed more than

3,000 instruments for rockets, satellites, space probes, and space station in collaboration with JAXA, ESA, and NASA.


Caution For safe and correct usage, please read the "Operation

Manual" prior to the use of the products. Specifications and designs are subject to change without

notice. Specifications and designs are based on the standard model.

Please contact us regarding further customization to suit your project’s needs.

This products may be subject to the application of the Foreign Exchange and Foreign Trade Act and other related laws and regulations in Japan. Customer agrees to comply with such regulations and acknowledges that it is their responsibility to obtain any required licenses to export, re-export, or import this products.

We shall not be liable for any damages arising out of or in connection with the use of specifications herein, including liability for lost profit, business interruption, or any other damages whatsoever.

The color of the product photography on catalog might be different from that of actual product because of printing.

Tokyo Branch: TOYOSU IHI BUILDING 10F, 1-1, Toyosu 3-chome, Koto-ku, Tokyo 135-8115, Japan Tel: +81-3-6204-8252 Fax: +81-3-6204-8888 Sales & Marketing Dept. Aerospace & Defense Systems Div.

Headquarters: 2223 Naganumamachi, Isesaki-shi, Gunma 372-8585, Japan Tel: +81-270-32-1117 Fax: +81-270-32-0988 Aerospace & Defense Systems Div.

www.meisei.co.jp/english E-mail: [email protected]

MSPA4-048 M2007 The specifications in this catalog are current as of July 2020.

Electrical characteristics

Frequency 8,025 MHz to 8,400 MHz

Symbol rate 100 Msymbol/s (typ.)

Standards CCSDS 131.2 or DVB-S2*1/S2X*2

Modulation QPSK, 8PSK, 16APSK, 32APSK,

and 64APSK

Error

correction Turbo coding (SCCC) or LDPC*1,2

Data rate 69 Mbps to 522 Mbps

RF power +33 dBm (QPSK to 32APSK)

+30 dBm (64APSK)

Bandwidth < 150 MHz

Filter Compliant with ITU regulations

TTC interface RS-422 level, UART

DC power

supply +18 V to +34 V, 22 W (typ.)

Physical characteristics

Dimensions 100 x 100 x 73 mm

Mass < 1,300 g

Ordering Information

MTX-540X-FM Flight model

MTX-540X-EM Engineering model

MTX-OPT-DATASOURCE Option: Test data source unit and software (USB 3.0 to Parallel LVDS)

MTX-OPT-SR50M Option: 50 Msymbol/s mode, (BW < 75 MHz, up to 269 Mbps)

MTX-OPT-DVBS2 Option: DVB-S2 mode, up to 32APSK

MTX-OPT-DVBS2X Option: DVB-S2X mode, up to 64APSK

MTX-OPT-BPF Option: External band pass filter for SFCG recommendation

(deep space)

MTX-OPT-PANT4 Option: Patch antenna

(Gain = 13.5 dBi, Size = 70 x 70 x 10 mm, Mass = 80 g)

SPECIFICATIONS


Data input interface

Standard Parallel LVDS

(CCSDS 130.12-G-1)

Clock input Up to 100 MHz

Data input 8 bits + Data_valid

Data rate Up to 800 Mbps

Flow control Data_request from

transmitter

Environment

Operational

temperature -40°C to +50°C

Vibration GSFC-STD-7000A,

Table 2.4-3

Shock GSFC-STD-7000A,

Figure 2.4-1

Radiation

tolerance > 10 krad

Design

lifetime 5 years in LEO

*1 MTX-OPT-DVBS2

*2 MTX-OPT-DVBS2X

Features Flight proven Lower cost using COTS parts The 2-way Doppler measurement function controls the transmission frequency

depending on the reception frequency of the command signal from the ground. 1Mbps high speed communication (QPSK) Control for switch of USB/QPSK transmission and switch of coherent（2-Way Doppler）

/incoherent mode is available Monitoring the status of the transceiver (transmission and reception status, internal

temperature and the setting status of each mode) In case only USB is required, it will be realized by the sole operation of the upper unit. Tolerant of the severe environment of small satellite ITAR free RoHS nonconformity Made in Japan

It will be installed on the small satellite and perform the command reception from the

ground, and the telemetry transmission to the ground using 2GHz wave band.

Outline Upper section : USB transceiver unit

Lower section : QPSK transmission unit

＊ This product was developed in the support of JAXA.

＊ Note that, with due to the rights of other relevant parties and/or depending on usage application and/or delivery place the

products may not be sold commercially distributed, leased or included in a part of product or system which intends to receive

benefits through the inclusion of the product.


SPECIFICATIONS

Items Performance

Re

ce

ivin

g

pe

rform

an

ce

Reception frequency 2 GHz band

Modulation PCM(NRZ-L)-PSK-PM

Receiving sensitivity ＜ -100 dBm

Sub carrier frequency 16 kHz

Command bit rate 4 kbps

US

B

tran

sm

iss

ion

pe

rform

an

ce

Transmission

frequency 2 GHz band

Modulation PCM(Biφ-L)-PM

Transmission output +10 dBm(Typ.)

Telemetry bit rate 16 kbps

QP

SK

tra

ns

mis

sio

n

pe

rform

an

ce

Transmission

frequency 2 GHz band

Modulation QPSK

Transmission output +27 dBm(Typ.)

Telemetry bit rate 1 Mbps

Oth

er p

erfo

rma

nc

e

Power supply voltage +17 to 35 VDC

Power consumption

＜ 2.8 W (standby)

＜ 3.8 W (USB transmission)

＜ 15 W (QPSK transmission)

Operating temperature

range -10 to +50℃

Dimensions 198 x 120 x 38.8 mm

(flange and screw not included)

Mass ＜ 1.65 kg

Lead time About 12 months after receiving orders.

Flight heritage SDS-4

SOCRATES











MSPA4-046 M2007


The specifications in this catalog are current as of July 2020.

Features Flight proven Lower cost using COTS parts QZSS and GPS receivable Digital synthesis of dual channel antenna input signal Positioning of the spacecraft regardless of the attitude by dual channel antenna The maximum length of cable is1.5m. GPS-R(1PC)/GPS-A(2PC) ITAR free RoHS nonconformity Made in Japan

GPS and QZSS receiver for micro and small satellites Dual GPS antenna enables positioning at any attitude Inner combination of signals from two antennas

Outline


SPECIFICATIONS











Items Performance

GPS-R

Number of channels 16

Number of antennas 2

GPS signal L1 C/A

1575.42 ± 1.023 MHz

Positioning accuracy ＜ 3 m (static state)

Time to fix Cold start: ＜ 15 min

Warm start: ＜ 1 min

Sensitivity ＜ -130 dBm at antenna terminal

Telemetry/command

interface Serial I/F (TIA/EIA-422 ITU-T V.11)

Telemetry Latitude, Longitude, Altitude, Position (3D), Velocity

(3D), Status, etc.

Supply voltage 5 V

Power consumption ＜ 2.5 W (except antenna)

Dimensions

Receiver : 107 x 131 x 31 mm

Antenna : 44 x 51 x 15 mm


Mass ＜ 500 g

Temperature range Operation : -20 to +60℃

Non-operation : -50 to +70℃

Vibration Random : 25.72 Grms (20 to 2000 Hz)

Radiation Tolerant to radiation environment of LEO altitude

Rigidity (first natural

frequency) 300 Hz

GPS-A

Reception frequency 1575.42 ± 1.023 MHz

Gain 26 dBi ± 6 dB ( -30 to + 85 ℃)

Output impedance 50Ω

Output VSWR ＞ 2.0

Power supply voltage DC 4.5 ±0.5 V

Consumption current 12 to 30mA


range -30 to +85℃

Storing temperature range -40 to +100℃

Other Lead time About 6 months after receiving orders.

Flight heritage ISS

MSPA4-049 M2007



Features

Outline 3-axis fluxgate magnetometer for attitude measurement

Flight proven Lower cost using COTS parts High stability, good linearity Analog voltage output Wide power supply range Compact, light weight and low power consumption ITAR free RoHS nonconformity Made in Japan


SPECIFICATIONS











Items Performance

Measurement range ±64000 nT

Alignment accuracy ±1°

Analog output voltage 0 to 5 V

Power supply voltage 15 V

Power consumption ＜ 1.1 W (15 V / normal temperature)



Mass ＜ 220 g

Operating

temperature range -30 to +60℃


Heritages SDS-4

＊ Above-mentioned specification is an example. The specifications will be customized to suit your request. ＊ This product was developed with the support of JAXA (Japan Aerospace Exploration Agency) ＊ Please take note that there is the possibility not to be able to sell the products mentioned herein depending on application and delivery place, concerning the rights related to technical information.

MSPA4-047 M2007



Features Flight proven Lower cost using COTS parts. Can be used for both of sunlight and eclipse. No cooling system required Suitable for Earth oriented micro-satellites ITAR free RoHS nonconformity Made in Japan

The Earth sensor is a device for determining the attitude of a micro satellite at an

altitude of about 500 km.

4 pieces of multi-pixel array of thermopile sensors detect Earth edge to calculate the

roll angle and the pitch angle. Its compact design is suitable for Micro-Satellites.

Outline


SPECIFICATIONS

Items Performance

Detector COTS based Thermopile Sensor

FOV 33 degrees x 4 arrays

Accuracy 4.125°

Weighting calculation around Earth edge: ~1.5°(reference)

Power voltage +5 V

Power consumption ＜ 1 W

Operating

temperature range -25 to +60 ℃

Weight ＜ 250 g


（flange and screw not included） Telemetry / command

interface RS485


Flight heritage SOCRATES











Theory of measurement

Position of Horizon Horizon of Thermo-pile array Output of Thermo-pile array

＊ This product was developed with the support of JAXA (Japan Aerospace Exploration Agency) ＊ Above-mentioned specification is an example. The specifications will be customized to suit your request.

MSPA4-050 M2007



Features Flight proven Lower cost using COTS parts Vibration and shock resistant for space Up to 5kV with a fixed HVPS and sweeping HVPS ITAR free RoHS nonconformity Made in Japan

This instrument is a HVPS (high voltage power supply) to be installed on scientific

satellite for supplying voltage to detectors in the space environment. It can be output

up to 0 to +5000 V / -5000 to 0 V with reference voltage(analog or digital).

Outline


SPECIFICATIONS











Items Performance

Output voltage range 0 to +5000 V / -5000 to 0 V

Max output current ＜ 100 μA

Output ripple voltage ＜ 100 mVp-p

Input voltage range +11.5 to +13.0 V (DC)/-11.5 to -13.0 V (DC)

Reference voltage range 0 to 5 V

Monitor output voltage range 0 to 5 V

Output current ＜ 0.5 W( I x V ),(V: output voltage)




Flight heritage ISS, Exposed Facility (MAXI)

Lunar explorer, SELENE/KAGUYA

Sweeping HVPS (+5000V)

We can also make sweeping type.

MSPA4-051 M2007



Features

Meisei Electric provides every size of magnetic torquers: for pico, nano, micro, small

satellites and CubeSat. Meisei’s magnetic torquers are designed in our original

technique and have a good balance of power consumption and mass. This model is

for 50 to 100 Kg satellite.

Outline

For 50 kg satellite (12 Am2 typ.)

For CubeSat (0.1 Am2 typ.)

Flight proven Lower cost using COTS parts 1 set of 3 torquers Optimal balance of power consumption and mass is realized Fully customizable: magnetic moment, dimensions, mechanical and electrical

interface ITAR free RoHS nonconformity Made in Japan


SPECIFICATIONS











Items Performance

Output magnetic moment 12 Am2 typ.

Power supply voltage 15 V

Power consumption 1W typ. (Nominal, 217Ω) / 12 Am2 typ.



Mass ＜ 500 g

Operating temperature range -30 to +60℃


Flight heritage

SDS-1

SDS-4

SOCRATES

＊ The specifications will be tailored to suit your needs. If you use more than for 100 Kg satellite, we would kindly ask you to pay for the option fee. Because of torque value change. ＊ This product was developed with the support of JAXA (Japan Aerospace Exploration Agency) ＊ Note that, with due to the rights of other relevant parties and/or depending on usage, application and/or delivery place, the product may not be sold, commercially distributed, leased or included in a part of product or system which intends to receive benefits through the inclusion of the product.

MSPA4-053 M2007



Features Simultaneous classification and energy measurement of electrons, protons, and

heavy particles. ITAR free RoHS nonconformity Made in JAPAN

Outline SPM can count space radiation, and it is used for a small satellite with an altitude of 400 to 500 km.* SPM identify the effect of the space radiation environment(TID,SEE etc.**) in the satellite orbit. *Customization is available

**Estimate only. SPM count the number of the energy particle(Electron, Proton, Heavy ion)


SPECIFICATIONS











Items Performance

Power supply voltage +12 VDC (45mAtyp.), -12 VDC (20mAtyp.), +5VDC (60mAtyp.)

Telemetry / command

interface RS-422

Line type / Energy range

Electron ：＞0.21 MeV (2CH)

Proton ： 5.5 to 300 MeV (6CH)

Heavy Ion ：＞7.12 MeV/n (2CH)

FOV ±41.2 deg



Mass ＜ 900 g (MLI included)


range -10 to +50 ℃

Power consumption ＜ 1.1 W

Data rate 370 bps (in the case of 1 sec integration time)

Lead time About 9 to 12 months after receiving orders.

Delivery time depends on availability of calibration test equipment.

Flight heritage RAPIS-1 (JAXA)

＊ Above-mentioned specification is an example. ＊ FOV is determined by satellite orbit. The specifications will be customized to suit your request. In the case we would kindly ask you to pay for the option fee.

MSPA4-055 M2007



Features Flight proven SHIROP was loaded by “TSUBAME" (SLATS). TSUBAME is the optical telescope

that takes the pictures of the land from the super low earth orbit (200～300km). Mission of the SHIROP is the technical demonstration that taking high-resolution

picture by the small size telescope. Covered with MLI Beta Cross RoHS nonconformity Made in Japan

The high-resolution Imaging system for Microsatellites Meisei Electric developed the SHIROP-E (SHIROP control unit) and took part of

the thermal control design for SHIROP-S (SHIROP sensor unit) and SHIRP-E.

Outline

SHIROP-S (SHIROP sensor unit)

SHIROP-E (SHIROP control unit)


SPECIFICATIONS











Items Performance

SHIROP-S

Size Φ 200 x 500 mm

Telescope Cassegrain

Mass ( nominal ) 11.5 Kg

GSD 1.8 m / altitude 600 km

Imaging range 10653 x 7000 m / altitude 600 km

Imaging system TDI

(Time Delay Integration)

Band User selectable

Flight heritage H-IIA F37: Super Low Altitude Test Satellite

"TSUBAME" (SLATS)

SHIROP-E Dimensions 227.5 x 127.5 x 96.2 mm


MSPA4-054 M2007



Features Flight proven Remote controlled from the ground and move autonomously The camera adopts existing drone technology. Exterior and inner structures were all manufactured by 3D-printing. Made in Japan

The first camera drone that can record video while moving in space

Meisei Electric Co., Ltd. cooperated with JAXA (Japan Aerospace Exploration

Agency) in the field of Body design Electric design Assembly Verification test

Outline

ⓒJAXA/NASA

Acquiring the capability to move anywhere at any time via autonomous flight and record images from any angle

Realizing "zero" photographing time by the onboard crew Enabling flight controllers and researchers on the ground to check the crew's work

from the same viewpoint as the crew

Objectives of Development


SPECIFICATIONS











Items Performance

Dimensions < 150 mm in diameter

(not including 3D marker )

Mass < 1 kg

(not including cables and 3D marker)

Localization

and control

Translational control Micro axial fans

Rotational control Triaxial reaction wheels and / or

Micro axial fans

Localization Image recognition with 3D Marker

Main Camera

Resolution 720 p (1280×720 pixels)

1080 p (1920×1080 pixels)

Frame rate 10 to 30 fps

Bit rate 16 kbps to 40 Mbps

Data format Photo / Movie (no audio)

Image stability Bandwidth

Pan: 1 Hz or less

Tilt and Roll: 0.3 Hz or less

Attitude stability ±1 degree/s or less

Data

transmission

Transmission method IEEE802.11a

Transmission rate 16 kbps to 40 Mbps

Power supply Lithium battery

Battery life Approx. 2 hours

(Rechargeable via USB connector)

＊ To develop this camera drone, Meisei Electric Co., Ltd. cooperated with

JAXA in the field of body design, electric design, assembly, and verification test. ⓒJAXA/NASA

MSPA4-052 M2007

ⓒJAXA/NASA



MEMO


MEMO














Documents

JAXA/NASA Products GuideBook · 2020. 9. 14. · ＊ This product was developed in the support of JAXA. ＊ Note that, with due to the rights of other relevant parties and/or depending